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US8910485B2 - Stoichiometric exhaust gas recirculation combustor with extraction port for cooling air - Google Patents

Stoichiometric exhaust gas recirculation combustor with extraction port for cooling air Download PDF

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Publication number
US8910485B2
US8910485B2 US13/087,463 US201113087463A US8910485B2 US 8910485 B2 US8910485 B2 US 8910485B2 US 201113087463 A US201113087463 A US 201113087463A US 8910485 B2 US8910485 B2 US 8910485B2
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US
United States
Prior art keywords
flow
exhaust gas
mixing zone
gas recovery
zone
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Application number
US13/087,463
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English (en)
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US20120260660A1 (en
Inventor
Gilbert Otto Kraemer
Sam David Draper
Kyle Wilson Moore
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Vernova Infrastructure Technology LLC
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US13/087,463 priority Critical patent/US8910485B2/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DRAPER, SAM DAVID, KRAEMER, GILBERT OTTO, Moore, Kyle Wilson
Priority to EP12164063.5A priority patent/EP2511496B1/fr
Priority to CN201210179128XA priority patent/CN102733955A/zh
Publication of US20120260660A1 publication Critical patent/US20120260660A1/en
Application granted granted Critical
Publication of US8910485B2 publication Critical patent/US8910485B2/en
Assigned to GE INFRASTRUCTURE TECHNOLOGY LLC reassignment GE INFRASTRUCTURE TECHNOLOGY LLC ASSIGNMENT OF ASSIGNOR'S INTEREST Assignors: GENERAL ELECTRIC COMPANY
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/08—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber for reducing temperature in combustion chamber, e.g. for protecting walls of combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/08—Purpose of the control system to produce clean exhaust gases
    • F05D2270/082—Purpose of the control system to produce clean exhaust gases with as little NOx as possible
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/09001—Cooling flue gas before returning them to flame or combustion chamber

Definitions

  • the present application relates generally to gas turbine engines and more particularly relates to a stoichiometric exhaust gas recirculation turbine system with a combustor having an extended flow sleeve so as to provide adequate cooling and extraction.
  • EGR exhaust gas recirculation
  • SEGR stoichiometric exhaust gas recirculation
  • the present application provides a stoichiometric exhaust gas recovery turbine system.
  • the stoichiometric exhaust gas recovery turbine system may include a main compressor for compressing a flow of ambient air, a turbine, and a stoichiometric exhaust gas recovery combustor.
  • the stoichiometric exhaust gas recovery combustor may include a combustion liner, an extended flow sleeve in communication with the main compressor, and an extraction port in communication with the turbine.
  • the extended flow sleeve receives the flow of ambient air from the main compressor so as to cool the combustion liner and then the flow of ambient air splits into an extraction flow to the turbine via the extraction port and a combustion flow within the combustion liner.
  • the present application further provides a method of operating a stoichiometric exhaust gas recovery turbine system.
  • the method may include the steps of providing an extended flow sleeve about a firing zone of a combustor, flowing ambient air along the extended flow sleeve about the firing zone so as to cool the firing zone, extracting a portion of the ambient airflow downstream of the firing zone, and flowing the remaining portion of the ambient airflow within the firing zone for combustion therein.
  • the present application further provides a stoichiometric exhaust gas recovery combustor for combusting a flow of ambient air and a flow of fuel.
  • the stoichiometric exhaust gas recovery combustor may include a mixing zone, a firing zone, an extend flow sleeve surrounding the mixing zone and the firing zone, and an extraction port positioned about the flow sleeve and downstream of the firing zone. The flow of ambient air flows through the extended flow sleeve to cool the firing zone and then splits into an extraction flow via the extraction port and a combustion flow into the mixing area.
  • FIG. 1 is a schematic view of a stoichiometric exhaust gas recirculation turbine system.
  • FIG. 2 is a side cross-sectional view of a stoichiometric exhaust gas recirculation combustor as may be described herein for use with a stoichiometric exhaust gas recirculation turbine system.
  • FIG. 1 shows an example of a stoichiometric exhaust gas recovery turbine system 10 .
  • the stoichiometric exhaust gas recovery turbine system 10 may include a main compressor 15 .
  • the main compressor 15 compresses an incoming flow of ambient air 20 .
  • the main compressor 15 delivers the compressed flow of ambient air 20 to a combustor 25 .
  • the combustor 25 mixes the compressed flow of ambient air with a compressed flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 .
  • the stoichiometric exhaust gas recovery turbine system 10 may include any number of combustors 25 .
  • the flow of combustion gases 35 is in turn delivered to a turbine 40 .
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the main compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • an external load 50 such as an electrical generator and the like.
  • Other components and other configurations may be used herein.
  • the stoichiometric exhaust gas recovery turbine system 10 also may include a stoichiometric exhaust gas recovery subsystem 55 .
  • the stoichiometric exhaust gas recovery subsystem 55 may include a stoichiometric exhaust gas recovery compressor 60 .
  • the stoichiometric exhaust gas recovery compressor 60 may be in communication with and driven by the shaft 45 .
  • the stoichiometric exhaust gas recovery subsystem 55 also may include a heat recovery steam generator 65 and a cooler 70 downstream of the turbine 40 .
  • Other components and other configurations may be used herein.
  • the flow of combustion gases 35 through the turbine 40 may contain only low levels of oxygen because of the equilibrium chemistry at the temperatures used for combustion.
  • the combustion gases 35 leaving the turbine 40 may be considered a low oxygen recirculation flow 75 .
  • the low oxygen recirculation flow 75 thus may be cooled in a recirculation loop 80 in the heat recovery steam generator 65 and the cooler 70 with the heat therein available for useful work.
  • the now cooled low oxygen recirculation flow 75 then may be compressed within the stoichiometric exhaust gas recovery compressor 60 and mixed with the flow of ambient air 20 and the flow of fuel 30 in the combustor 25 for combustion therein.
  • the stoichiometric exhaust gas recovery turbine system 10 and the components described herein are for the purposes of example only.
  • the stoichiometric exhaust gas recovery turbine system 10 may have many other components and other configurations.
  • a portion of the ambient airflow 20 may be extracted at the combustor 25 and sent to the turbine 40 via a combustion extraction line 85 .
  • About thirty percent (30%) or more of the ambient airflow 20 may be diverted so as to ensure stoichiometric operation therein.
  • the amount of the diversion may depend upon the flow needed to replace the oxidizer such as air or oxygen. Other types and amounts of air extractions may be used herein.
  • FIG. 2 shows a stoichiometric exhaust gas recovery combustor 100 as may be described herein.
  • the stoichiometric exhaust gas recovery combustor 100 may be used with the stoichiometric exhaust gas recovery turbine system 10 described above and the like.
  • the stoichiometric exhaust gas recovery combustor 100 may include one or more fuel nozzles 110 therein.
  • the fuel nozzle 110 may be greater in length as compared to typical fuel nozzles for the reasons described below.
  • the fuel nozzle 110 may be in communication with a fuel inlet 120 .
  • the stoichiometric exhaust gas recovery combustor 100 may mix the flow of ambient air 20 , the flow of fuel 30 , and the low oxygen recirculation flow 75 and then ignite the mixture to produce the flow of combustion gases 35 .
  • the stoichiometric exhaust gas recovery combustor 100 also may include a combustion liner 130 .
  • the combustion liner 130 may define a mixing zone 140 and a firing zone 150 therein.
  • the fuel nozzle 110 may be positioned within and extends through the mixing zone 140 into the firing zone 150 .
  • the combustion liner 130 , the mixing zone 140 , and the firing zone 150 may be longer in length as compared to those typically found in a conventional combustor.
  • a low oxygen recirculation inlet 160 also may be in communication with the mixing zone 140 for the low oxygen recirculation flow 75 .
  • An extended flow sleeve 170 may surround the combustion liner 130 and may define an ambient air path 180 therein for the flow of ambient air 20 .
  • the extended flow sleeve 170 and the recirculated gas may be in communication with the main compressor 15 .
  • the flow of ambient air 20 in the ambient air path 180 of the extended flow sleeve 170 cools the combustion liner 130 about the firing zone 150 while providing the flow of ambient air 20 to the mixing zone 140 .
  • the extended flow sleeve 170 also may be longer in length as compared to those of conventional compressors to ensure adequate cooling of the combustion liner 130 about the firing zone 150 . Increasing the length of the flow sleeve 170 thus requires the increased length of the other components described above.
  • a casing 190 may surround the extended flow sleeve 170 and the combustion liner 130 .
  • a transition piece 200 may be positioned downstream of the firing zone 150 .
  • An extraction port 210 may be positioned about the casing 190 and in communication with the ambient air path 180 of the extended flow sleeve 170 .
  • the extraction port 210 may be in communication with the turbine 40 via the extraction line 85 .
  • the extraction port 210 may be positioned downstream of the firing zone 150 such that all or most of the ambient airflow 20 passes about the firing zone 150 for cooling therewith.
  • the extended flow sleeve 170 may end via one or more flow sleeve apertures 220 .
  • the one or more flow sleeve apertures 220 may be in communication with the mixing zone 140 .
  • the extraction port 210 and the one or more flow sleeve apertures 220 thus split the ambient airflow 20 after cooling into an extraction flow 230 that passes through the extraction port 210 to the turbine 40 via the extraction line 85 and a combustion flow 240 that flows into the mixing zone 140 via the one or more flow sleeve apertures 220 for combustion therein.
  • Other configurations and other components may be used herein.
  • the volume of the extraction flow 230 may be determined by the size, number, and position of the flow sleeve apertures 220 in the extended flow sleeve 170 as compared to the extraction port 210 .
  • the desired percentage of the ambient airflow 20 thus may be extracted to the turbine 40 via the extraction port 230 . Thirty percent (30%) or more of the ambient airflow 20 thus may be extracted.
  • the remaining combustion flow 240 then mixes in the mixing zone 140 via the flow sleeve apertures 220 with the low oxygen recirculation flow 75 and ignited with the flow of fuel 30 within the firing zone 150 . Because of the extended flow sleeve 170 , the desired cooling flow within the ambient air path 180 is maintained about the combustion liner 130 near the firing zone 150 .
  • the stoichiometric exhaust gas recovery combustor 100 thus meets increased air extraction requirements without diminishing the cooling flow along the combustion liner 130 about the firing zone 150 . Likewise, the stoichiometric exhaust gas recovery combustor 100 meets component lifetime requirements despite the increased extraction.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
US13/087,463 2011-04-15 2011-04-15 Stoichiometric exhaust gas recirculation combustor with extraction port for cooling air Active 2033-10-01 US8910485B2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US13/087,463 US8910485B2 (en) 2011-04-15 2011-04-15 Stoichiometric exhaust gas recirculation combustor with extraction port for cooling air
EP12164063.5A EP2511496B1 (fr) 2011-04-15 2012-04-13 Chambre de combustion avec recirculation des gaz d'échappement stoechiométrique
CN201210179128XA CN102733955A (zh) 2011-04-15 2012-04-13 化学计量的排气再循环燃烧器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/087,463 US8910485B2 (en) 2011-04-15 2011-04-15 Stoichiometric exhaust gas recirculation combustor with extraction port for cooling air

Publications (2)

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US20120260660A1 US20120260660A1 (en) 2012-10-18
US8910485B2 true US8910485B2 (en) 2014-12-16

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EP (1) EP2511496B1 (fr)
CN (1) CN102733955A (fr)

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CN102733955A (zh) 2012-10-17
EP2511496B1 (fr) 2020-09-23
EP2511496A2 (fr) 2012-10-17
EP2511496A3 (fr) 2018-02-14
US20120260660A1 (en) 2012-10-18

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